EP2133265B1 - Hubschrauber - Google Patents

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Publication number
EP2133265B1
EP2133265B1 EP08425408A EP08425408A EP2133265B1 EP 2133265 B1 EP2133265 B1 EP 2133265B1 EP 08425408 A EP08425408 A EP 08425408A EP 08425408 A EP08425408 A EP 08425408A EP 2133265 B1 EP2133265 B1 EP 2133265B1
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EP
European Patent Office
Prior art keywords
wall
helicopter
inlet
end edge
airflow
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP08425408A
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English (en)
French (fr)
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EP2133265A1 (de
Inventor
Fabio Nannoni
Dante Ballerio
Alessandro Scandroglio
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Agusta SpA
Original Assignee
Agusta SpA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Agusta SpA filed Critical Agusta SpA
Priority to DE602008002151T priority Critical patent/DE602008002151D1/de
Priority to PT08425408T priority patent/PT2133265E/pt
Priority to PL08425408T priority patent/PL2133265T3/pl
Priority to EP08425408A priority patent/EP2133265B1/de
Priority to AT08425408T priority patent/ATE477177T1/de
Priority to RU2009121507/11A priority patent/RU2499736C2/ru
Priority to US12/481,215 priority patent/US8113461B2/en
Priority to JP2009139226A priority patent/JP5524513B2/ja
Priority to KR1020090051478A priority patent/KR101586008B1/ko
Priority to CN2009101639079A priority patent/CN101612991B/zh
Publication of EP2133265A1 publication Critical patent/EP2133265A1/de
Application granted granted Critical
Publication of EP2133265B1 publication Critical patent/EP2133265B1/de
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/08—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D7/00—Arrangement of military equipment, e.g. armaments, armament accessories or military shielding, in aircraft; Adaptations of armament mountings for aircraft
    • B64D7/08—Arrangement of rocket launchers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C2025/325—Alighting gear characterised by elements which contact the ground or similar surface  specially adapted for helicopters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters

Definitions

  • the present invention relates to a helicopter.
  • Helicopters are known substantially comprising a fuselage; a main rotor rotating about a first axis and fitted to a top portion of the fuselage; and an antitorque rotor located at the tail end of the helicopter and rotating about a second axis crosswise to the first.
  • Known helicopters also comprise at least one engine; and a transmission for transmitting motion from the engine to the main rotor.
  • the engine has an intake conduit for a first airflow of fresh air from the outside; and an exhaust conduit for externally discharging high-temperature burnt gas.
  • the helicopter also comprises a transmission housing; and an inlet connecting the housing to the outside to produce a second airflow of fresh air by which to cool the transmission either directly or with the interposition of a radiator.
  • thermodynamic efficiency of the engine and transmission cooling efficiency are affected by the attitude, and particularly the yaw angle, of the helicopter.
  • Variations in yaw angle also affect the degree of turbulence in the first airflow, thus affecting the thermodynamic efficiency of the engine.
  • a need is felt within the industry to achieve as constant a flow as possible of the first and second airflow, and to minimize turbulence in the first airflow over a wide attitude range, so as to achieve optimum thermodynamic efficiency of the engine and effectively cool the transmission within said range.
  • US 4830312 discloses a helicopter in which combustion air and cooling air for an oil cooler and an intercooler is drawn through a common inlet grill.
  • GB1201096 discloses inlet arrangements in a turboprop engine installation.
  • Number 1 in Figure 1 indicates a helicopter substantially comprising a fuselage 2 with a nose 5; a main rotor 3 fitted to the top of fuselage 2 and rotating about an axis A; and a tail rotor 4 fitted to a tail fin projecting from fuselage 2 at the opposite end to nose 5, and rotating about a second axis crosswise to axis A.
  • Helicopter 1 comprises two engines 6 (only one shown in Figure 6 ) housed in respective housings defined by a supporting body 7 and located alongside respective sides 8 of fuselage 2.
  • Helicopter 1 comprises two transmissions 9 (only one shown in Figure 6 ) connecting the output shafts of respective engines 6 to a shaft 10 (only shown partly in Figures 3 , 4 , 5 ) for rotating main rotor 3 about axis A. More specifically, the output shafts of engines 6 extend along respective axes B (only one shown in Figure 6 ).
  • Each engine 6 performs in the same way as an open-thermodynamic-cycle gas turbine, and substantially comprises ( Figure 6 ) :
  • Each engine 6 also comprises :
  • helicopter 1 advantageously comprises an air intake 20, in turn comprising :
  • air intakes 20 are located alongside respective sides 8, and project towards nose 5 from a front end 25 of supporting body 7 facing nose 5.
  • end 25 of supporting body 7 has two edges 26 alongside fuselage 2; and two edges 27 extending crosswise to fuselage 2 and between respective facing ends of edges 26.
  • Air intakes 20 are preferably integral with each other.
  • Air intakes 20 obviously being identical, only one is described below for the sake of simplicity.
  • air intake 20 comprises ( Figures 2 to 5 ) :
  • the deflecting means are defined by edge 30 which performs substantially in the same way as the leading edge of a wing to divert the first and second airflow onto surfaces 32 and 31 respectively of wall 29.
  • contour of wall 29 is also defined by two edges 33 converging in edge 30 in the direction from end 25 to edge 30.
  • Main portion 37 of wall 35 extends from end portion 36 towards nose 5 of fuselage 2.
  • End portion 36 is larger than main portion 37 in a direction parallel to edge 27, and is smaller than main portion 37 lengthwise of fuselage 2.
  • End portion 36 of each wall 35 is integral with end portion 36 of the other wall 35 ( Figure 2 ).
  • Main portion 37 has a curved first end edge 38 cooperating with surface 32; and a curved second edge 39 opposite edge 38 and at a distance from surface 32.
  • edge 38 comprises an end portion 40 parallel to edge 30 and interposed between edge 30 and end portion 36; and two portions 41 converging towards edge 30 in the direction from end portion 36 to edge 30.
  • Portions 41 are located on opposite sides of portion 40.
  • Edge 39 is curved and substantially comprises an arc-shaped portion 42 on the side facing end 25; and a portion 43 elongated towards edge 30, connected to portion 42, and located on the side facing portion 40.
  • portion 42 extends along an arc of roughly 180°, and portion 43 is located outside the sector subtended by portion 42.
  • edge 39 extends obliquely with respect to axis A.
  • the contour of inlet 21 comprises an arc-shaped first portion 45; and a second portion 46 defining a tip located outside the circumference defined by portion 45.
  • Portion 45 is located on the side facing end 25, and portion 46 on the side facing portion 40.
  • portion 46 comprises two segments converging in the direction from portion 45 to portion 40, and having first ends connected to respective ends of portion 45, and second ends opposite the first ends and connected to each other.
  • Portion 46 is located outside the sector defined by portion 45.
  • Inlet 21 is closer than edge 39 to surface 32.
  • main portion 37 of edge 35 extends at increasing distances from surface 32 in the direction from edge 38 to edge 39, and at decreasing distances from surface 32 in the direction from edge 39 to inlet 21 ( Figure 3 ).
  • the thickness of main portion 37 increases in the direction from edge 38 to edge 39, and decreases in the direction from edge 39 to inlet 21.
  • the projection of the contour of inlet 21 onto surface 32 lies within the projection of the contour of edge 39 onto surface 32.
  • the main portion 52 of wall 50 comprises two surfaces 53 defining respective inlets 22 and converging in a rounded edge 54 in the direction from end portion 51 to edge 30 of wall 29.
  • Inlets 22 in the example shown are rectangular and open into respective conduits 55 ( Figure 5 ) terminating inside housing 23 of transmission 9 ( Figure 6 ).
  • edge 54 is interposed between end 25 and edge 30.
  • the guide means of each air intake 20 comprise :
  • each path Q is bounded laterally by a relative side 8 and by a relative surface 31, and each path P extends on the opposite side of relative wall 29 to relative path Q.
  • Engine 6 also comprises a tapping device 18 surrounding compressor 11 and for drawing off a quota (indicated I in Figure 6 ) of the first airflow upstream from compressor 11, and feeding quota I to nozzle 15.
  • a tapping device 18 surrounding compressor 11 and for drawing off a quota (indicated I in Figure 6 ) of the first airflow upstream from compressor 11, and feeding quota I to nozzle 15.
  • Fresh-air quota I thus mixes with the hot burnt gas flowing through nozzle 15 to cool the exhaust gas from opening 17 and so reduce the overall radiation emitted by helicopter 1 in the infrared frequency.
  • conduit 16 also functions as an ejector by activating, by means of the gas accelerated in nozzle 15, an airflow which originates in housing 23, cools transmission 9 to a certain extent, and eventually mixes with the burnt gas inside conduit 16.
  • airflow F strikes edges 30 of walls 29, and is diverted by edges 30 to form first and second airflows along respective paths P, Q.
  • first airflows flow along surfaces 32 of relative walls 29 and along the portions of walls 35 interposed between surfaces 32 and respective inlets 21, and finally through inlets 21 and along intake conduits 12 of engines 6.
  • devices 18 draw off respective quotas I of the first airflows upstream from respective compressors 11, and feed them directly to nozzles 15. More specifically, the drawn-off quotas I are less than the respective remaining portions (indicated L in Figure 6 ) of the respective first airflows.
  • the remaining portions L of the first airflows are compressed by respective compressors 11, and react with the fuel inside respective combustion chambers 13 to produce hot pressurized burnt gas, which expands inside respective turbines 14 and flows along nozzles 15 to rotate the output shafts of engines 6 about respective axes A.
  • Transmissions 9 transmit motion from the output shafts of engines 6 to the drive shaft 10 of rotor 3.
  • the second airflows flow along surfaces 31 of relative walls 29, along the portions of surfaces 53 interposed between inlets 22 and relative edges 54, and finally through inlets 22 and along conduits 55 to housings 23 of transmissions 9, where they cool transmissions 9 either directly or by means of a radiator.
  • edge 30 of each air intake 20 divides the airflow F on it into a first and second airflow, which reach respective inlets 21, 22 along separate paths P, Q.
  • inlets 22 are located on the fuselage 2 side, and inlets 21 on the opposite side to fuselage 2, the turbulence generated by aerodynamic interaction between helicopter 1 and airflow F is more predominant in the second airflows than in the first.
  • Paths P and Q being separate prevents this turbulence from being transmitted to the first airflows.
  • the first airflow along conduit 12 and predominantly drawn by compressor 11 is therefore substantially laminar, and so improves the efficiency of engines 6 over a wide range of yaw angles of helicopter 1.
  • engines 6 since air intake by engines 6 is constant, in quantity and flow conditions, over a wide range of yaw angles of helicopter 1, engines 6 have similar operating temperatures, and can therefore be coupled in temperature to improve the overall performance of helicopter 1.
  • Another advantage of separating paths P and Q lies in the second airflows being undisturbed by the first, and so being substantially constant over a wide range of yaw angles of helicopter 1, thus greatly reducing the risk of in-mission overheating of transmission 9.
  • Walls 35, 50 having no sharp curves at respective inlets 21, 22 greatly reduces pressure losses in the first and second airflow.
  • air intake 20 provides, with a single device, for drawing in both first and second airflows for supplying compressors 11 of engines 6 and cooling transmissions 9 and the exhaust gas respectively.
  • helicopter 1 may have one engine 6 and one air intake 20.
  • Walls 53 may have one inlet 22.
  • inlets 21, 22 and conduits 12, 16 may be other than as shown.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • General Details Of Gearings (AREA)
  • Medicines Containing Material From Animals Or Micro-Organisms (AREA)
  • Inorganic Insulating Materials (AREA)
  • Supercharger (AREA)
  • Toys (AREA)
  • Jet Pumps And Other Pumps (AREA)

Claims (12)

  1. . Hubschrauber (1) umfassend:
    - ein Triebwerk (6) mit einer Verbrennungsluft-Einlassleitung (12);
    - einen funktionell mit dem Triebwerk (6) verbundenen Hauptrotor (3)
    - eine funktionell zwischen besagtem Hauptrotor (3) und besagtem Triebwerk (6) angeordnete in einem Gehäuse (23) angeordnete Übertragungseinheit (9);
    gekennzeichnet durch wenigstens einen Lufteinlass (20), welcher seinerseits
    - wenigstens einen ersten Einlass (21), welcher strömungsmäßig mit der Einlassleitung (12) verbunden ist,
    - wenigstens einen zweiten Einlass (22), welcher strömungsmäßig mit besagtem Gehäuse (23) verbunden ist,
    - Ablenkmittel, welche im Betriebszustand derart mit einem Luftstrom (F) zusammenwirken, dass der Luftstrom (F) in einen ersten und zweiten Luftstrom unterteilt werden, und
    - Leiteinrichtungen (31, 32, 37, 53) zu Strömungsführung des besagten ersten Luftstroms entlang eines ersten Strömungswegs (P) von besagten Ablenkmitteln (30) zu dem besagten ersten Einlass (21) und Strömungsführung des besagten zweiten Luftstroms entlang eines vom ersten Strömungsweg (P) getrennten zweiten Strömungswegs (Q), welcher von den Ablenkmitteln (30) zu besagtem zweiten Einlass (22) verläuft,
    aufweist.
  2. . Hubschrauber nach Anspruch 1, dadurch gekennzeichnet, dass der besagte Lufteinlass (20) eine die besagten Ablenkmittel (30) bildende erste Wand (29) umfasst.
  3. . Hubschrauber nach Anspruch 2, dadurch gekennzeichnet, dass die besagten Ablenkmittel von einer ersten Randkante (30) der besagten ersten Wand (29) gebildet werden.
  4. . Hubschrauber der mit einem Rumpf (2) versehenen Bauart nach Anspruch 2 oder 3, durch gekennzeichnet, dass der besagte zweite Strömungsweg (Q) zwischen der besagten ersten Wand (29) und dem besagten Rumpf (2) und der besagte erste Strömungsweg (P) auf der gegenüberliegenden Seite der besagten ersten Wand (29) zu dem besagten Rumpf (2) verläuft
  5. . Hubschrauber nach Anspruch 4, dadurch gekennzeichnet, dass der besagte Lufteinlass (20) eine zweite Wand (35) und eine dritte Wand (50) aufweist, welche den besagten ersten bzw. zweiten Einlass (21, 22) bilden; wobei die besagte dritte Wand (50) zwischen einer ersten Oberfläche (31) der besagten ersten Wand (29) und dem besagten Rumpf (2) verläuft und die besagte zweiten Wand (35) von einer zweiten, der ersten Oberfläche (31) gegenüberliegenden Oberfläche (32) der besagten ersten Wand (29) vortritt, und die besagten Leiteinrichtungen (31, 32, 37, 53) von der besagten ersten und zweiten Oberfläche (31, 32) der besagten ersten Wand (29) durch den zwischen der besagten zweiten Oberfläche (32) und dem besagten ersten Einlass (21) zu verlaufenden Abschnitt der zweiten Wand (35) und durch den Abschnitt der besagten dritten Wand (50) gebildet wird, welcher zwischen der besagten ersten Oberfläche (31) und dem besagten zweiten Einlass (22) verläuft.
  6. . Hubschrauber nach Anspruch 5, dadurch gekennzeichnet, dass die besagte zweite Wand (35) eine zweite Randkante (38), welche zumindest teilweise mit der besagten zweiten Oberfläche (32) der besagten ersten Wand (29) zusammenwirkt, und eine der besagten zweiten Randkante (38) gegenüberliegende freie dritte Randkante (39) aufweist, wobei der besagte erste Einlass (21) in einem Abstand von der besagten zweiten Oberfläche (32) verläuft, welcher geringer als der Abstand zwischen der besagten dritten Randkante (39) und der besagten zweiten Oberfläche (32) ist.
  7. . Hubschrauber nach Anspruch 6, dadurch gekennzeichnet, dass sich die rechtwinklig zur zweiten Oberfläche (32) gemessene Dicke der besagten zweiten Wand (35) in Richtung von der besagten zweiten Randkante (38) zu der besagten dritter Randkante (39) vergrößert und in Richtung von der besagten dritten Randkante (39) zu dem besagten ersten Einlass (21) verringert.
  8. . Hubschrauber nach einem der Ansprüche 3 bis 7, dadurch gekennzeichnet, dass die Kontur des besagten ersten Einlasses (22) einen ersten winkelförmigen Abschnitt (46) und einen zweiten bogenförmigen Abschnitt (45) aufweist, welcher auf der gegenüberliegenden Seite des besagten ersten Winkelabschnitt (46) zum freien Ende der ersten Randkante (30) der besagten ersten Wand (29) verläuft, wobei der besagte erste Winkelabschnitt (46) in Richtung von der besagten ersten freien Randkante (30) der besagten ersten Wand (29) in Richtung zum besagten zweiten bogenförmigen Abschnitt (45) divergiert.
  9. . Hubschrauber nach einem der Ansprüche 5 bis 8, dadurch gekennzeichnet, dass die besagte dritte Wand (50) eine freie vierte Randkante (54) aufweist und eine dritte und vierte Oberfläche (53), welche in Richtung zu der besagten vierten Randkante (54) konvergieren, wobei die besagte dritte und vierte Oberfläche (53) jeweils einen zugeordneten zweiten Einlass (22) bilden.
  10. . Hubschrauber nach Anspruch 9, dadurch gekennzeichnet, dass besagte vierte Randkante (54) der besagten dritten Wand (50) zwischen der besagten freien ersten Randkante (30) der besagten ersten Wand (29) und den besagten zweiten Einlässen (22) angeordnet ist.
  11. . Hubschrauber nach einem der Ansprüche 5 bis 10, dadurch gekennzeichnet, dass die besagte erste, zweite und dritte Wand (29, 35, 50) miteinander integral ausgebildet sind.
  12. . Hubschrauber nach einem der vorausgehenden Ansprüche, durch gekennzeichnet, dass das Triebwerk
    - einen Verdichter (11), welche im Betriebszustand einen Teil des durch den besagten ersten Einlass (21) und die besagte Einlassleitung (12) strömenden Luftstroms ansaugt;
    - eine Brennkammer (13), welche im Betriebszustand mit von dem besagten Verdichter (11) gelieferter Druckluft beaufschlagt wird und unter Erzeugung von hoch temperierten Abgasen eine Reaktion der besagten Druckluft mit einem Brennstoff verursacht;
    - eine Turbine (14), welche im Betriebszustand das besagte Abgas entspannt;
    - eine Düse (15) zur Veränderung der Strömungsgeschwindigkeit der in der besagten Turbine (14) expandierten Abgase und
    - eine das besagte Abgas abführende, in Strömungsrichtung hinter der besagten Düse (15) angeordnete Auslassleitung (16); umfasst,
    - wobei der besagte Hubschrauber (1) so ausgebildet ist, dass er außerdem eine Abzweigleitung zur Entnahme eines Anteils (I) des besagten ersten Luftstroms in Strömungsrichtung vor dem besagten Verdichter (11) aufweist und den besagten Anteil (I) in Strömungsrichtung hinter die besagte Turbine (14) führt, um den besagten Anteil (I) mit den aus der Turbine (14) austretenden Abgasen zu mischen.
EP08425408A 2008-06-10 2008-06-10 Hubschrauber Active EP2133265B1 (de)

Priority Applications (10)

Application Number Priority Date Filing Date Title
DE602008002151T DE602008002151D1 (de) 2008-06-10 2008-06-10 Hubschrauber
PT08425408T PT2133265E (pt) 2008-06-10 2008-06-10 Helicóptero
PL08425408T PL2133265T3 (pl) 2008-06-10 2008-06-10 Helikopter
EP08425408A EP2133265B1 (de) 2008-06-10 2008-06-10 Hubschrauber
AT08425408T ATE477177T1 (de) 2008-06-10 2008-06-10 Hubschrauber
RU2009121507/11A RU2499736C2 (ru) 2008-06-10 2009-06-08 Вертолет
US12/481,215 US8113461B2 (en) 2008-06-10 2009-06-09 Helicopter
JP2009139226A JP5524513B2 (ja) 2008-06-10 2009-06-10 ヘリコプタ
KR1020090051478A KR101586008B1 (ko) 2008-06-10 2009-06-10 헬리콥터
CN2009101639079A CN101612991B (zh) 2008-06-10 2009-06-10 直升飞机

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08425408A EP2133265B1 (de) 2008-06-10 2008-06-10 Hubschrauber

Publications (2)

Publication Number Publication Date
EP2133265A1 EP2133265A1 (de) 2009-12-16
EP2133265B1 true EP2133265B1 (de) 2010-08-11

Family

ID=39761026

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08425408A Active EP2133265B1 (de) 2008-06-10 2008-06-10 Hubschrauber

Country Status (10)

Country Link
US (1) US8113461B2 (de)
EP (1) EP2133265B1 (de)
JP (1) JP5524513B2 (de)
KR (1) KR101586008B1 (de)
CN (1) CN101612991B (de)
AT (1) ATE477177T1 (de)
DE (1) DE602008002151D1 (de)
PL (1) PL2133265T3 (de)
PT (1) PT2133265E (de)
RU (1) RU2499736C2 (de)

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EP2995556A1 (de) 2014-09-12 2016-03-16 AIRBUS HELICOPTERS DEUTSCHLAND GmbH Flugzeug mit Lufteinlass für ein Strahltriebwerk

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CA2830938C (en) 2011-04-28 2015-03-24 Bell Helicopter Textron Inc. Self-aligning inlet plenum system for rotorcraft
US9051057B2 (en) * 2011-12-28 2015-06-09 Embraer S.A. Aircraft air inlet diverter assemblies with improved aerodynamic characteristics
FR2986275B1 (fr) * 2012-02-01 2016-07-01 Turbomeca Procede d'ejection de gaz d'echappement de turbine a gaz et ensemble d'echappement de configuration optimisee
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EP2853493B1 (de) * 2013-09-30 2016-08-10 AIRBUS HELICOPTERS DEUTSCHLAND GmbH Hubschrauber mit Triebwerklufteinlassanordnung
US9574497B2 (en) * 2013-10-08 2017-02-21 Bell Helicopter Textron Inc. Engine mounted inlet plenum for a rotorcraft
US9656760B2 (en) * 2013-11-07 2017-05-23 Sikorsky Aircraft Corporation Variable geometry helicopter engine inlet
US9586692B2 (en) * 2014-04-14 2017-03-07 Sikorsky Aircraft Corporation Engine inlet configuration
EP3056423B1 (de) * 2015-02-16 2017-12-13 AIRBUS HELICOPTERS DEUTSCHLAND GmbH Flugzeug mit einem rumpf der mindestens einen innenbereich und einen bereich zur antriebsunterbringung definiert
US10662859B1 (en) * 2016-05-02 2020-05-26 Northwest Uld, Inc. Dual flap active inlet cooling shroud
KR102174214B1 (ko) * 2019-01-02 2020-11-04 한국항공우주산업 주식회사 엔진 공기흡입구용 방빙장치
JP7235582B2 (ja) * 2019-05-07 2023-03-08 株式会社Subaru 冷却ダクト
US12208909B2 (en) * 2019-09-08 2025-01-28 Textron Innovations Inc. Aircraft with bifurcated air inlet
JP7333267B2 (ja) * 2019-12-26 2023-08-24 川崎重工業株式会社 ヘリコプター
RU2737979C1 (ru) * 2020-03-23 2020-12-07 Константин Борисович Махнюк Вертолет
EP3904217B1 (de) * 2020-04-27 2022-09-28 LEONARDO S.p.A. Schwebeflugfähiges luftfahrzeug

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EP2995556A1 (de) 2014-09-12 2016-03-16 AIRBUS HELICOPTERS DEUTSCHLAND GmbH Flugzeug mit Lufteinlass für ein Strahltriebwerk

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CN101612991B (zh) 2013-05-22
JP2009298399A (ja) 2009-12-24
DE602008002151D1 (de) 2010-09-23
KR101586008B1 (ko) 2016-01-15
PL2133265T3 (pl) 2011-01-31
CN101612991A (zh) 2009-12-30
EP2133265A1 (de) 2009-12-16
US20100230530A1 (en) 2010-09-16
JP5524513B2 (ja) 2014-06-18
RU2499736C2 (ru) 2013-11-27
KR20090128345A (ko) 2009-12-15
US8113461B2 (en) 2012-02-14
PT2133265E (pt) 2010-10-18
RU2009121507A (ru) 2010-12-20
ATE477177T1 (de) 2010-08-15

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